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Chinese Journal of High Pressure Physics  > 2007  >  21(3): 253-258 .
BAI Jing-Song, TANG Mi, HUA Jing-Song, LI Ping, TAN Hua. An Improved of Experimental Hypervelocity Launcher and Simulation[J]. Chinese Journal of High Pressure Physics, 2007, 21(3): 253-258 . doi: 10.11858/gywlxb.2007.03.006
Citation: BAI Jing-Song, TANG Mi, HUA Jing-Song, LI Ping, TAN Hua. An Improved of Experimental Hypervelocity Launcher and Simulation[J]. Chinese Journal of High Pressure Physics, 2007, 21(3): 253-258 . doi: 10.11858/gywlxb.2007.03.006
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An Improved of Experimental Hypervelocity Launcher and Simulation

doi: 10.11858/gywlxb.2007.03.006

  • Laboratory for Shock Wave and Detonation Physics Research, Institute of Fluid Physics, CAEP, Mianyang 621900, China

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  • Corresponding author: BAI Jing-Song
  • Received Date: 25 Aug 2006
  • Rev Recd Date: 08 Nov 2006
  • Issue Publish Date: 05 Sep 2007
    Abstract
  • A numerical simulation method for calculation of the three-stage light-gas gun impacts on launch flier to hypervelocity is presented. Based on multi-fluid volume of fraction (VOF) and parabolic piecewise method (PPM), a multi-fluid parabolic piecewise method (MFPPM) shock wave physics code is developed to calculate the experimental hypervelocity launchers. To verify and validate our code of MFPPM, some experimental hypervelocity launchers from Sandia National Laboratories are simulated, and the numerical results of flier velocity are excellent in agreement with that experiment (the maximal relative error is 1.07%). Experiment and simulation results of our experiment on the three-stage light-gas gun are given (the maximal relative error is 1.04%). To satisfy well of the high-pressure equation of state (EOS) data measurement, an improved design model from the computation is presented.

     

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    • References(5)
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